Abstract: A lightweight passive attenuator (1) for spacecraft includes two omega cross-section rings (2), placed symmetrically and defining a gap therebetween, and being the main load path of the light passive attenuator (1). A plurality of damper elements (3) are placed in the gap defined between the two omega cross-section rings (2), and not in the main load path of the light passive attenuator (1), such that the omega cross-section rings (2) and the damper elements (3) are assembled at their ends by attachment elements. The omega cross-section rings (2) have a protruding central part (5) with a plurality of holes (6) for connection with adjacent structures (7, 8) of the spacecraft.

Abstract: A lightweight passive attenuator (1) for spacecraft includes two omega cross-section rings (2), placed symmetrically and defining a gap therebetween, and being the main load path of the light passive attenuator (1). A plurality of damper elements (3) are placed in the gap defined between the two omega cross-section rings (2), and not in the main load path of the light passive attenuator (1), such that the omega cross-section rings (2) and the damper elements (3) are assembled at their ends by attachment elements. The omega cross-section rings (2) have a protruding central part (5) with a plurality of holes (6) for connection with adjacent structures (7, 8) of the spacecraft.

Abstract: A device used for providing dynamic isolation and damping of dynamic vibrations, in a passive way, originated in the launch vehicle of a space shuttle and reaching the payload or satellite. The device comprises a plurality of identical elementary unit elements, such that the device is designed in a modular way, allowing the individual modularity of each of the elementary unit elements. Each of the elementary unit elements is tailored and designed individually, and the complete device can be designed for each particular application and payload needed as a function of each of the elementary unit elements allowing an easy design and lower costs, for a wide range of payload applications. Each elementary unit element comprises a spring component and a damping component, such that the functionalities provided for each component are separated and can be individually tailored, thus providing a device having a wider range of adaptation capabilities.

Abstract: A launcher and satellite connection-separation apparatus for launching and satellite vehicles has a band-clamp assembly of a band with an inner channel in which clamps are located in a sliding manner for application to rings interfacing between the vehicles, and a union-separation device on ends of the band for radially tightening the band and controlling opening of the band in first and second phases such that the ends of the band shift in contact with the rings for dissipating by friction elastic energy corresponding to the tightening of the band and separate from the rings until reaching a parking position.

Abstract: A launcher and satellite connection-separation apparatus comprising a band (11) with an inner channel in which a plurality of clamps (13) are located in a sliding manner, which clamps are applied on the rings (15, 17) making up the joining interface between both vehicles, means (19) for radially tightening the band (11)-clamps (13) assembly and a union-separation device (41, 61, 71) of the ends (7, 9) thereof including, together with locking (47) and unlocking (48) means, a mechanism allowing a controlled opening of the band (11) in two phases: in the first phase its ends (7, 9) shift keeping in contact with the rings (15, 17), the elastic energy corresponding to the tightening of the band (11) being dissipated by friction; in the second phase the band (11) separates from the rings (15, 17) until reaching its parking position.

Abstract: The attenuation device of the present invention comprises a surface of revolution (11) of circular cross section, such that a set of slots (14) is distributed between the sides of the surface of revolution (11) and adapted to confine an elastic material (15) within the limits defined by the slots (14), generating a structural labyrinth for load passage from a lower interface of the surface of revolution (11) to an upper interface.

Abstract: A system for the modification of the rigidity and damping properties of structural joints comprises at least an intermediate structure (3) to receive, on both sides, two structures (1, 2) to be coupled; releasable blocking means (6) to immobilize, in a coupled condition, said two structures to be coupled and said intermediate structure; first and second sets of bistable components (7, 8), the structural resistance features of the components of the first set being different from those of the second set; the components of the first set being internally connected to one of said structures to be coupled and to said intermediate structure; the components of the second set being internally connected to one and other of said structures to be coupled; said bistable components being in an unstable condition when all the mentioned structures are coupled together. The invention is applicable to the field of space vehicles.